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The European
Small Launcher
VEGA
BR-257
The European
Small Launcher
Vega brochureApril27 5/15/07 11:36 AM Page 1
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The European small launcher, called ‘Vega’, will make its inaugural
flight from Europe’s Spaceport in French Guiana before the end of
2008. This will be an important milestone in the implementation of
the European strategy in the launcher sector and the guarantee of
access to space for Europe, as endorsed by the ESA Council at
Ministerial Level in 2003. The exploitation of this new ESA-
developed launcher will widen the range of European launch
services on offer and will improve launch flexibility by providing a
more adapted response for a wide range of European institutional
space missions, as well as an optimised family of launchers to serve
commercial market needs.
By being developed as an ESA programme, Vega is taking
significant advantage of launcher technologies developed
previously at European level, particularly in the solid-propulsion
and avionics fields. Furthermore, Vega constitutes a trail-blazer not
only because its development benefits from a single overall
programme management structure involving ESA and national
space agencies, in this case ASI and CNES, but also because its
industrial organisation already relies on a launcher industrial prime
contractor (ELV).
For its exploitation, Vega will be operated by Arianespace from the
Guiana Space Centre (CSG). This approach will foster additional
synergies in the exploitation of ESA-developed launchers from
Europe’s Spaceport.
Antonio Fabrizi
Director of Launchers, ESA
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VegaThe European Small Launcher
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VegaThe European Small Launcher
Contents
The Background 4
The Market 5
The Mission 6
The Organisation 8
The Launch Vehicle 10
The Ground Segment 16
The Road to Exploitation 18
2
Contents
The Background 4
The Market 5
The Mission 6
The Organisation 8
The Launch Vehicle 10
The Ground Segment 16
The Road to Exploitation 18
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ESA has elaborated a strategy for the
launcher sector in Europe targeted at
preserving the objectives of guaranteed
access to space and commercial success in
the new global environment, as well as
being consistent with current European
strategic, economic, cultural and political
interests.
The first objective of the European strategy
is to guarantee affordable access to space
for Europe through a family of launchers
providing the flexibility and
competitiveness needed to respond
optimally to institutional and commercial
needs. In this respect, the Ariane launch
system will continue to serve primarily the
heavy-payload class of missions, while the
Vega launch system will serve the small-
payload class mainly for low Earth orbits.
The addition of the exploitation of Soyuz
from the Guiana Space Centre (CSG) will
complete the range of launch services on
offer by catering for the medium-payload
class.
The second element is to foster
international cooperation, in order to open
new market opportunities for European
Industry, to consolidate the guarantee of
access to space, and to maximise
technological cooperation. In parallel,
technologies need to be prepared for the
timely development of new systems in
order to meet the long-term competition
(2015-2020).
The last element of the strategy is to
maintain the industrial capabilities needed
to ensure the continued high quality of the
launch services and operations offered to
customers by the European Spaceport in
French Guiana.
The BackgroundThe Background
The History
The Vega Programme has its origins back in the 1990’s, when studies were performed in several European countries toinvestigate the possibility of complementing the range of performance offered by the Ariane family of launchers with acapability for smaller payloads. The Italian Space Agency (ASI) and Italian industry not only developed concepts, but alsobegan pre-development work based on their established knowhow in solid propulsion. Vega officially became an ESAProgramme in June 1998, when the Agency succeeded in Europeanising the national ASI small-launcher programme – in the meantime called ‘Vega’ – as a co-operative project with other Member States within the ESA framework.
For more background information see:
http://www.esa.int/launchers
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The growing need for smaller satellites
Two main factors, namely changes in space-
programme policies and the evolution in
satellite technologies, explain the recent
reduction in the sizes and the weights of
many satellites, especially in the field of
Earth Observation. These smaller satellites
can be divided into three categories:
Micro-satellites : up to 300 kg
Mini-satellites : from 300 to 1000 kg
Small satellites : from 1000 to 2000 kg.
The micro/mini-satellite market is almost
exclusively driven by institutional
programmes, with Earth Observation and
scientific missions representing the most
significant sector. The orbits required are
mainly Sun Synchronous Orbits (SSO) and
Low Earth Orbits (LEO).
The Vega-addressable market therefore
currently stands at around 3 to 5 missions
per year, split between single launches for
small and mini-satellites and multiple
launches for one mini-satellite and/or
several micro-satellites.
A wide range of launch services
ESA’s launcher strategy is founded on the
principle of offering the nations of Europe
guaranteed access to space, implying that
Europe should be able to launch by its own
means any size or category of mission.
Vega, together with the mid-class Soyuz
launcher and the heavy-class Ariane-5
launcher, will ensure that a full range of
launch services will indeed be available for
Europe, thereby allowing optimised mission
planning based on the exact performance
required in each case for an affordable cost.
The standard performances of the
European launcher family when operated
from the European Spaceport are as
follows:
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The MarketThe Market
The 21st century has begun with a significant interest in smaller satellites and therefore
in the need for appropriate launch services. In order to maintain its competitiveness in
the World market, Europe is therefore expanding the range of missions that it can handle
by developing the Vega small launcher.
Launcher Vega Soyuz Ariane-5 Generic Ariane-5 ECA
Orbit SSO/LEO GTO GTO GTO
Payload mass, kg 1500 (700 km) 3000 6600 10000
SSO/LEO: Sun Synchronous Orbit/Low Earth Orbit , GTO: Geostationary Transfer Orbit
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Vega is designed to cope with a wide range
of missions and payload configurations in
order to respond to different market
opportunities and therefore provide the
flexibility needed by the customers. In
particular, it might offer configurations able
to handle payloads ranging from a single
satellite up to one main satellite plus six
micro-satellites. Vega is compatible with
payload masses ranging from 300 kg to
2500 kg, depending on the type and
altitude of the orbit required by the
customer. In this respect, it can provide
launch services for a
wide variety of
missions, from equatorial
to Sun-synchronous.
The benchmark for Vega’s in-
orbit launch capacity is 1500 kg
into a 700 km-altitude polar orbit.
The complete performance matrix is
shown in the accompanying table.
The MissionThe Mission
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A typical launch can be divided into three
main phases:
• The first phase corresponds to the launch
vehicle’s propulsive ascent phase into a
low elliptical trajectory (sub-orbital
profile). During this phase, the fairing will
be jettisoned, once the aero-thermal
fluxes are low enough for the
unprotected payload.
• The second phase corresponds to the
circularization of the orbit and satellite(s)
release and injection into the required
orbit(s), with the specified parameters.
• The third and final phase of the mission
is usually devoted to the removal of the
satellite(s) from operational orbit to
comply with international regulations
concerning space debris.
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1000
1100
1200
1300
1400
1500
1600
1700
1800
1900
2000
2100
2200
2300
0 10 20 30 40 50 60 70 80 90 100 110
Paylo
ad
Mass [
kg
]
300 km
1500 km
700 km
1200 km
500 km
VEGA LV PERFORMANCEREQUIREMENT
Vega brochureApril27 5/15/07 11:36 AM Page 7
Vega is an ESA Optional Programme
managed by the Vega Department within
the Agency’s Directorate of Launchers. The
development activities are organised into
three projects addressing:
- The Launch Vehicle
- The P80 (1st-stage solid-rocket motor)
- The Ground Segment.
The Programme is managed jointly by an
Integrated Project Team (IPT) composed of
staff from ESA, ASI and CNES, based at
ESRIN in Frascati, Italy, for the Launch
Vehicle and Ground Segment, and at CNES
in Evry, France, for the P80 motor. It
therefore benefits from the technical
support and expertise of both ESA and
CNES.
The industrial organisation for Vega is
considered a forerunner of the future
organisation for European launcher
development and is based on having a
Prime Contractor for each project: ELV (I) for
the Launch Vehicle, AVIO (I) with delegation
to Europropulsion (I, F) for the P80, and
Vitrociset (I) for the Ground Segment.
The complete development effort is based
on two programme declarations, one for
the Launch Vehicle including the Ground
Segment, and another for the P80 motor.
The OrganisationThe Organisation
ESA/IPT
Launch Vehicle(ESRIN)
P80(CNES Evry)
Ground Segment(ESRIN)
Launch VehiclePrime Contractor
ELV (I)
P80Prime Contractor
Avio (I)
FirstSubcontractor
EUP (I, F)
Ground SegmentPrime Contractor
Vitrociset (I)
ESA/IPT
Launch Vehicle(ESRIN)
P80(CNES Evry)
Ground Segment(ESRIN)
Launch VehiclePrime Contractor
ELV (I)
P80Prime Contractor
Avio (I)
FirstSubcontractor
EUP (I, F)
Ground SegmentPrime Contractor
Vitrociset (I)
Launch Vehicle + Ground SegmentBelgium : 5.63%France : 15%Italy : 65%Netherlands : 2.75-3.5%Spain : 6%Sweden : 0.80%Switzerland 1.34%
P80Belgium : 19%France : 66%Italy : 9.3% + contribution from IndustryNetherlands : 4.5%
Member State Contributions to the Vega Programme
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Launch Vehicle and P80
The industrial Prime Contractor for the Vega launch
vehicle is the company ELV SpA, 30% of which is
owned by ASI (Italian Space Agency) and 70% by
AVIO.
Ground Segment
Under the umbrella of the Ground-System Prime
Contractor Vitrociset, the work is divided across
three main ‘subsystems’, with an industrial
contractor responsible for each of them. These
subsystems are:
• the Civil Infrastructure, which covers the
refurbishment of the existing infrastructure (the
former Ariane-1 pad, ELA1) as well as the
construction of the new infrastructure,
including civil works, air conditioning and
energy installations. The main contractor is
Vitrociset (F), with Cogel (I) responsible for the
system engineering.
• the Mechanical, Fluids and General Means,
which includes the design, manufacture and
installation of the mobile gantry, launcher
interfaces, gas supplies, communication
systems and low-voltage installation. The main
contractor is Carlo Gavazzi Space (I). Oerlikon
Contraves Italy (I) is responsible for the
mechanical part, Telematic Solutions (I) for the
low-voltage installation, and Cegelec (F, NL) for
the fluid installations.
• the Control Systems, which include the Vega
Control Centre, the computer centre, and
monitoring and control of Ground Segment
house-keeping processes. Vitrociset (I) is the
main subsystem contractor, with Dataspazio (I),
Laben (I) and GTD (E) as subcontractors
responsible for control-system packages.
CNES is supporting the development of the Vega
Ground System in terms of design, systems
engineering, configuration management,
interfacing with CSG and test campaigns. CNES is
also responsible for the Vega-related modifications
needed to the Kourou installations, such as the
tracking, localisation and telemetry systems.
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Thales, Zodiac, Galileo Avionica, CRISA, SAAB,SAFTAVUM Avionics
EADS CASASpain, AVUM Structure and AVUMT3Skirt
AvioItaly, AVUM Propulsion System
Contraves SpaceSwitzerland, Fairing
EADS CASASpain, Adapter
AvioItaly, AVUM (stage integration and test)
AvioItaly, 3rd Stage (production, integration and test)
AvioItaly, 2nd Stage (production, integration and test)
SABCABelgium, 3rd Stage TVC
Oerlikon Contraves Italia (OCI)Italy, 2/3 Interstage
Dutch SpaceThe Netherlands, 1/2 Interstage
SABCABelgium, 2nd Stage TVC
SABCABelgium, 2CT: Interstage Skirt
SABCABelgium, 1st Stage TVC
SNECMA Propulsion SolidFrance, Nozzle
Stork Product EngineeringThe Netherlands, Igniters of Stages 1-2
AvioItaly, 1st Stage (stage integration and test)
EuropropulsionFrance, P80FW Motor
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Vega is a single-body launcher composed
of three solid-propellant stages and a
liquid-propellant upper module. It is
approximately 30 metres high, has a
maximum diameter of 3 metres, and weighs
a total of 137 tons at lift-off. It has three
main sections, namely the Lower
Composite, the Restartable Upper Module
and the Payload Composite.
The Lower Composite consists of three
solid-propellant stages:
- 1st stage: P80-FW / 88 tons of propellant
- 2nd stage: Z23 (Zefiro23) / 23 tons of
propellant
- 3rd stage: Z9 (Zefiro9) /10 tons of
propellant
plus the four stage-interfacing structures.
The Restartable Upper Module or 4th stage,
known as AVUM (Altitude and Vernier
Upper Module), hosts:
- the AVUM Propulsion Module
- the AVUM Avionics Module.
The Payload Composite that accommodates
the satellite(s) is composed of:
- the fairing
- the payload/launcher interface structure
(adaptor 937, dual carrying structure,
dispenser, etc.).
The Lower Composite
The motors of the three solid-propellant
stages – P80, Z23 and Z9 – benefit from the
strong experience acquired by Europe over
the years in the field of solid propulsion.
Their technology is derived from the Zefiro-
16 motor, which has already performed
three firing tests (in June 1998, June 1999
and December 2000) with good results.
Each motor is composed of:
- A carbon-epoxy filament-wound
monolithic case protected by low-
density thermal insulation packed with
micro-spheres (EPDM).
- The solid propellant HTPB 1912 (Finocyl-
type grain shape with star section on
nozzle side).
- A nozzle (3-D carbon/carbon throat,
flexible joint for a maximum deflection,
carbon phenolic exhaust cone).
- A thrust-vector control system driven by
two electro-actuators that operate the
movable nozzle, and a local control unit
providing pitch and yaw control during
the flight of each stage (located in the
inter-stage structures).
The Launch VehicleThe Launch VehicleC
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P80 TVC on the test stand
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Each equipped stage also includes a
pyrotechnic ignition subsystem, a safety
subsystem, and interfaces to the other
stages or, for the P80, the ground segment
by means of the inter-stage structures.
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P80 FW Zefiro23 Zefiro9Burn time (s) 107 77 105Vacuum specific impulse(s) 279.5 288 294.5
Max. vacuum thrust (kN) 3040 1200 330
MEOP (bar) 95 106 85.7
Nozzle expansion ratio 16 25 60.8
Nozzle deflection angle (deg) ± 6.5 ± 6.5 ± 6.0
Attitude control Pitch & Yaw Pitch & Yaw Pitch & Yaw
Main Features of the P80 Motor
The improvement of solid-propulsion capabilities by the adoption of advanced technologies is one of the building blocks ofthe European Launcher Strategy. The development activities have two primary objectives: firstly the qualification of the Vegafirst stage, representing the first step towards a new generation of European solid-rocket motors, and secondly thedemonstration of many of the technologies necessary to guarantee the Ariane-5 solid-rocket booster’s competitiveness. TheP80 motor is tailored to the Vega small launcher, but its scale is also representative for validating technologies applicable at alater stage to a new generation of Ariane-5 solid boosters.
Component: P80 new technologyCase: CFRP monolithic carbon fibre, 3 m diameterPropellant grain: Monolithic Finoxil, aft starInsulation: EG1LDB3 low-density EPDM-based rubber Nozzle throat: 3D C/C new low-cost materialExit cone: Composite, structural carbon phenolicFlex joint: Self-protected/low-torqueTVC actuator: Electro-mechanical
Maximum reduction of recurring costs is a driving parameter at alllevels of the solid-rocket motor’s design (subsystems, components,equipment, ground infrastructure, operations, etc.). A significantreduction with respect to the current metal-case boosters is a specificgoal for both the Vega first stage and the new-generation Ariane-5booster.
Interstage 1/2
Interstage 2/3
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Z9 igniter under test
P80 firing test in CSG (French Guiana)
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P80 and Z23 in Vega facilities Co
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The Restartable Upper Module
The Altitude and Vernier Upper Module
(AVUM) has two different sections, one
hosting the propulsion elements (AVUM
Propulsion Module) and one dedicated to
the vehicle equipment bay (AVUM Avionics
Module).
The liquid-propulsion system consists of a
single-chamber engine fed with NTO and
UDMH propellants at an inlet pressure of
30 bars. The propellants are stored in two
identical titanium tanks (142 litres/6 bars)
pressurised in flight by a gaseous-helium
vessel (88 litres/310 bars). The total
propellant load will be between 250 and
500 kg depending on the type of launch to
be performed.
The AVUM Propulsion Module provides
attitude control and axial thrust during the
final phases of Vega’s flight to fulfil the
following functions:
- roll control during all flight phases
- attitude control during the coasting and
in-orbit phases
- correction of axial velocity error due to
solid-rocket motor performance scatter
- generation of the velocity change
required for orbit circularisation
- satellite pointing
- satellite-release manoeuvres
- empty-stage de-orbiting.
AVUM Avionics Module
The avionics system is composed of both
hardware and software and its architecture
is based on a non-redundant approach,
except for the safety functions. To keep the
development and recurring costs to a
minimum, Vega’s avionics are largely
adapted from existing hardware and/or
components already under development.
For the same reason, particular attention
has been paid to defining the most
appropriate architecture for the avionics
subsystems, with the baseline consisting of
a centralised approach somewhat similar to
the concept used for Ariane-5.
The electrical system has four main
subsystems:
- Power Supply and Distribution
- Telemetry
- Localisation and Safeguard
- Flight Control and Mission Management.
AVUMBurn time (s) 317IgnitionVacuum specific impulse(s) 315.2
Max, Vacuum thrust (N) 2450
Number of restarts 5
Nozzle deflection angle (deg) ± 10.0
Attitude control Roll control during Z9 and AVUM flight
Orbital flight control 3-axis or spin-up
Equipped AVUM
Onboard computer
Safeguard Master Unit
The avionics Multi-Function Unit
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CH Vega fairing
The fairing
The launcher/satellite interface structure
The Safeguard subsystem is fully redundant,
in order to comply with launch-safety
requirements. For the other subsystems,
failure detection and means of recovery
have been implemented, where relevant, in
order to improve the launcher’s reliability.
The Flight Control subsystem will use an on-
board programmable flight computer, an
inertial measurement unit (derived directly
from that used on Ariane-5), and thrust-
vector control electronics for guidance,
navigation and control. A multi-functional
box will deliver electrical commands for
mission management, and stage and
payload separation on receipt of signals
from the on-board computer. The Telemetry
subsystem will be based on Ariane-5
elements, as it must be compatible with
existing ground-station standards and
protocols.
For the Safeguard subsystem, the Ariane-5
tracking architecture will be applied,
reusing already developed components
(transponders, antennas). The neutralisation
functions will be managed via new
Safeguard Master Units (SMUs) and
Safeguard Remote Units (SRUs) located in
the stages.
The Payload Composite
The fairing
The dimensions of the fairing define the
usable payload volume of the launcher. It is
composed of two carbon-fibre-reinforced
plastic shells with an aluminium
honeycomb structure, which are jettisoned
during flight after the separation of the
second stage. Separation of the two halves
of the fairing is ensured by a horizontal and
vertical separation system that has already
been used on the Ariane-4 launcher and
proved to be highly reliable.
Vega’s fairing also provides the interfaces
required for preparing the payload for
flight, including access doors, which can be
radio-transparent, an electrical umbilical
interface, and if needed a radio-frequency
repeater.
The launcher/satellite interface structure
The Adaptor 937 on Vega is a standard
launcher/satellite interface used on the
European launchers. It is a 60 kg, cone-
shaped carbon-fibre structure, with a
diameter of 937 mm at the separation plane
between launcher and satellite. The
standard version is equipped with a
separation system and two brackets for
electrical connectors. Optional hardware
can be added for specific missions at the
customer’s request.
The separation system consists of a clamp-
band set, four separation springs, and two
separation-feedback micro-switches. The
four separation springs ensure an
equilibrated separation push between
launcher and satellite, and the two micro-
switches provide confirmation of
separation.
Additional payload adapters/dispensers are
foreseen for multi-payload missions.
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The European Spaceport
Vega will benefit from the exceptional
location and existing launch infrastructure
of the European Spaceport at Kourou in
French Guiana. This French Overseas
Department lies close to equator on the
Atlantic coast of South America (latitude: 2
to 6 deg North / longitude: 50 deg West).
The choice of French Guiana to launch Vega
meets one of the programme’s main
requirements, namely to provide a high-
quality launch service (the Spaceport’s
launch-preparation facilities have a
worldwide reputation for excellence in the
space industry) whilst limiting costs (re-use
of ELA1 civil works and sharing of
preparation facilities).
The Spaceport will ultimately accommodate
launch-preparation facilities for Soyuz, as
well as those for Vega and Ariane-5. It will
also provide the necessary launch-support
infrastructure such as payload-preparation
facilities, transport, flight tracking, flight
data processing for post-flight analysis, and
meteorological data. A dedicated launch
zone is foreseen for each type of launcher,
but the payload-preparation complex
(EPCU) will be shared.
The Ground SegmentThe Ground Segment
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The Vega Facilities
Vega’s dedicated Ground Segment
comprises the Launch Zone (ZLV: Zone de
Lancement Vega) and the Operational
Control Centre.
The Launch Zone
The Vega Launch Zone is being built on the
site in the old ELA1 zone (previously used
for Ariane-1), and consists primarily of two
elements: a fixed infrastructure (the bunker)
and a mobile building (the gantry).
The bunker mainly comprises:
- The launch table, which ensures that the
launcher maintains its vertical position
and provides the interface with the
exhaust ducts.
- The umbilical mast, which ensures
continuity of the launcher’s and
payload’s thermal conditioning and
power supply until the very last moment,
as well as correct disconnection of those
systems from the launcher during lift-off.
- The exhaust ducts through which the
burning gases are channeled when the
motor is ignited on the launch pad.
- The four anti-lightning masts.
- Various premises such as safety room,
fluid room, gantry connection room, etc.
The mobile gantry provides the
infrastructure necessary for integration of
the launcher, such as hoisting devices for
the erection of the stages, platforms to
access to the different levels of the
launcher, connection and supply facilities,
fuelling installations for the fourth-stage
AVUM, safety systems, etc. The gantry is
rolled-back before launch, prior to the final
countdown.
The Operational Control Centre
The Operational Control Centre for Vega will
be located in the CDL3 building (Launch
Control Centre No.3, built for Ariane-5),
which allows there to be independent
operational and monitoring systems
dedicated to Vega as well as a sharing of
launch-site components with the other
launchers.
Payload Preparation Complex (EPCU)
Complementing some original CNES
facilities and others built later for the Ariane
development programme, ESA has
constructed a satellite-preparation complex
halfway between the Technical Centre and
the launch site. It will be used for satellite
and control equipment unpacking,
mechanical inspections, and check-out of
the various platform and payload
subsystems. It will also be used for the final
integration of the payload composite
before its transfer to the mobile gantry for
hoisting onto the top of the launcher.
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The Vega Launch Zone
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The qualification flight that will conclude
the Vega development phase managed
by ESA is planned to take place in the
second half of 2008.The development
logic is based on an incremental
verification approach based on
analysis, simulation and testing.
The various tests have been
designed to ensure verification
of the proper behaviour of the
launch vehicle during all
phases of its flight, under
conditions as close as
possible to the real ones.
The tests are scheduled
to progress from the
verification of each
single unit to a
global functional
verification.
ESA will be
responsible for the
qualification of the
launch service as overseer
of the development phase,
and also for sustaining the
qualification status throughout the
exploitation phase, when the facilities will
be handed over to the Vega Operator.
After the ground qualification and
successful in-flight demonstration of the
launcher’s suitability for various missions,
Arianespace will be responsible for Vega’s
commercialisation and launch operations. It
will therefore be responsible for all the
promotional, marketing and commercial
activities. It will procure vehicles from the
manufacturer according to market needs
and customer constraints, with an expected
launch rate of up to four flights per year.
It will also be responsible for the
management and maintenance of the
Vega Launch Zone facilities.
The Road to ExploitationThe Road to Exploitation
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The Vega Production Prime Contractor, ELV (I),
will be responsible for the definition
and organisation of the production of the
launch vehicles in accordance with the
procurement plan established by the Vega
Operator. ELV will also integrate the launch
vehicles at the European Spaceport.
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Arianespace
Arianespace is a leading global commercial launch-service provider, holding more than 50 percent of the World market forsatellite launches to geostationary transfer orbit (GTO). It was created as the first European commercial space-transportationcompany in 1980 and has signed launch contracts for more than 250 satellite payloads. Arianespace is also responsible forthe production, operation and marketing of the Ariane-5 launchers, and will be the commercial operator for Soyuz at Kourou.
Vega at ESRIN
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� ESA Headquarters8-10 rue Mario-Nikis75738 Paris Cedex 15Tel. (33) 1.53.69.71.55Fax (33) 1.53.69.76.90
� ESTEC NoordwijkThe NetherlandsTel. (31) 71.565.3006Fax (31) 71.565.6040
� ESOC DarmstadtGermanyTel. (49) 6151.90.2696Fax (49) 6151.90.2961
� EAC CologneGermanyTel. (49) 2203.60.010Fax (49) 2203.60.0166
� ESRIN FrascatiItalyTel. (39) 06.941.80.260Fax (39) 06.941.80.257
BR-257 April 2007, 2nd Imprint
Prepared by: Renato Lafranconi & Miguel Lopez
Vega Programme Dept., ESA Directorate of Launchers
Published by: ESA Publications
ESTEC, PO Box 299
2200 AG Noordwijk, The Netherlands
Editor: Bruce Battrick
Design and Layout: Jules Perel
Copyright: © 2007 European Space Agency
ISSN: 0250-1589
ISBN: 92-9092-446-2
Price: 10 Euro
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